ATE551498T1 - Kanalwand für ein gebläse eines gasturbinenmotors - Google Patents

Kanalwand für ein gebläse eines gasturbinenmotors

Info

Publication number
ATE551498T1
ATE551498T1 AT10161135T AT10161135T ATE551498T1 AT E551498 T1 ATE551498 T1 AT E551498T1 AT 10161135 T AT10161135 T AT 10161135T AT 10161135 T AT10161135 T AT 10161135T AT E551498 T1 ATE551498 T1 AT E551498T1
Authority
AT
Austria
Prior art keywords
damper
containment casing
intake section
gas turbine
turbine engine
Prior art date
Application number
AT10161135T
Other languages
English (en)
Inventor
Richard Brooks
Kenneth Udall
Richard Stretton
Original Assignee
Rolls Royce Plc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce Plc filed Critical Rolls Royce Plc
Application granted granted Critical
Publication of ATE551498T1 publication Critical patent/ATE551498T1/de

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rigid Pipes And Flexible Pipes (AREA)
AT10161135T 2009-05-05 2010-04-27 Kanalwand für ein gebläse eines gasturbinenmotors ATE551498T1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB0907580.5A GB0907580D0 (en) 2009-05-05 2009-05-05 A duct wall for a fan or a gas turbine engine

Publications (1)

Publication Number Publication Date
ATE551498T1 true ATE551498T1 (de) 2012-04-15

Family

ID=40792158

Family Applications (1)

Application Number Title Priority Date Filing Date
AT10161135T ATE551498T1 (de) 2009-05-05 2010-04-27 Kanalwand für ein gebläse eines gasturbinenmotors

Country Status (4)

Country Link
US (1) US8506234B2 (de)
EP (1) EP2256302B1 (de)
AT (1) ATE551498T1 (de)
GB (1) GB0907580D0 (de)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011005025A1 (de) * 2011-03-03 2012-09-06 Siemens Aktiengesellschaft Resonatorschalldämpfer für eine radiale Strömungsmaschine, insbesondere für einen Radialverdichter
US9664062B2 (en) * 2011-12-08 2017-05-30 Siemens Energy, Inc. Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system
US9534505B2 (en) 2012-07-23 2017-01-03 United Technologies Corporation Integrated nacelle inlet and metallic fan containment case
DE102014218350A1 (de) 2014-09-12 2016-03-17 Rolls-Royce Deutschland Ltd & Co Kg Schalldämpfende Anordnung für eine Triebwerksgondel und Triebwerksgondel mit einer solchen Anordnung
US10422280B2 (en) 2017-03-07 2019-09-24 United Technologies Corporation Fan flutter suppression system
US10428685B2 (en) 2017-03-07 2019-10-01 United Technologies Corporation Flutter inhibiting intake for gas turbine propulsion system
US10612464B2 (en) 2017-03-07 2020-04-07 United Technologies Corporation Flutter inhibiting intake for gas turbine propulsion system
US10941708B2 (en) 2017-03-07 2021-03-09 Raytheon Technologies Corporation Acoustically damped gas turbine engine
US10428765B2 (en) 2017-03-07 2019-10-01 United Technologies Corporation Asymmetric multi degree of freedom flutter damper
US10619566B2 (en) 2017-03-07 2020-04-14 United Technologies Corporation Flutter damper for a turbofan engine
EP3372814B1 (de) * 2017-03-07 2022-05-04 Raytheon Technologies Corporation Asymmetrischer flatterdämpfer mit mehreren freiheitsgraden
US10415506B2 (en) * 2017-03-07 2019-09-17 United Technologies Corporation Multi degree of freedom flutter damper
EP3372813B8 (de) * 2017-03-07 2021-04-07 Raytheon Technologies Corporation Flatterdämpfer mit mehreren freiheitsgraden
US10539156B2 (en) 2017-03-07 2020-01-21 United Technologies Corporation Variable displacement flutter damper for a turbofan engine
FR3083214A1 (fr) * 2018-06-28 2020-01-03 Airbus Operations Nacelle d'un ensemble propulsif d'aeronef comportant une pluralite d'elements amortisseurs entre une partie avant et une partie principale, et ensemble propulsif d'aeronef associe

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2090334B (en) 1980-12-29 1983-11-16 Rolls Royce Damping flutter of ducted fans
US4484856A (en) * 1981-12-21 1984-11-27 United Technologies Corporation Containment structure
US4934899A (en) * 1981-12-21 1990-06-19 United Technologies Corporation Method for containing particles in a rotary machine
US6206631B1 (en) 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
GB2365945B (en) * 2000-08-16 2004-02-11 Rolls Royce Plc A vibration damping system and a method of damping vibrations
US6499940B2 (en) 2001-03-19 2002-12-31 Williams International Co., L.L.C. Compressor casing for a gas turbine engine
GB0410778D0 (en) * 2004-05-13 2004-06-16 Rolls Royce Plc Blade arrangement
FR2903732B1 (fr) 2006-07-12 2008-09-12 Airbus France Sas Entree d'air pour turbomoteur d'aeronef.
US7721525B2 (en) * 2006-07-19 2010-05-25 Rohr, Inc. Aircraft engine inlet having zone of deformation

Also Published As

Publication number Publication date
EP2256302B1 (de) 2012-03-28
EP2256302A1 (de) 2010-12-01
US8506234B2 (en) 2013-08-13
GB0907580D0 (en) 2009-06-10
US20100284788A1 (en) 2010-11-11

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